Landing gear casing provided with a dissociated structure

Abstract

A reduced-volume casing for a landing gear including a chassis for fixing and taking up loads, to which the landing gear is exposed and an envelope-type structure arranged on the chassis for taking up pressurization forces. The chassis can include, in particular, a frame which is even to the output opening of the landing gear and is provided with beams used for receiving means for maintaining the fastening bearings of the gear and also including polygons which are used for receiving the fastening bearings of the gear manoeuvring strut and are fixed to the beams, wherein the beams and polygons form a lattice structure.

1. A reduced volume landing gear casing for aircraft landing gear, said casing comprising:
 a chassis to ensure the securing and take up or absorption of landing gear stresses comprising a frame flush with an opening through which the landing gear extends, the frame comprising parallel beams flush with the opening and to which the landing gear is attached; and 
 an envelope structure joined at least to the parallel beams, to take up or absorb pressurization stresses. 
 
     
     
       2. A landing gear casing according to  claim 1 , comprising bearings received by the parallel beams for attaching the landing gear to the parallel beams. 
     
     
       3. A landing gear casing according to  claim 2 , wherein the chassis includes polygons for receiving bearings of a strut for manoeuvring the landing gear, said polygons secured to the parallel beams, wherein the parallel beams and the polygons form a lattice structure. 
     
     
       4. A landing gear casing according to  claim 3  wherein the polygons comprise an arm attached to the strut and at least one rod holding the arm, said arm and said rod attached to the parallel beams, wherein a bearing securing the strut is received at tops of the polygons separated from the parallel beams. 
     
     
       5. A landing gear casing according to  claim 2  wherein the envelope structure includes a contour that joins the frame on an inside of an aircraft comprising the landing gear casing. 
     
     
       6. A landing gear casing according to  claim 2  wherein the chassis includes end cross beams that form a front wall and a rear wall of the landing gear casing. 
     
     
       7. A landing gear casing according to  claim 6  wherein the parallel beams are connected to said front and rear walls by square angle irons. 
     
     
       8. A landing gear casing according to  claim 2  wherein the parallel beams comprise a U iron that receives in its hollow section a corner iron for connecting parts of open frames of a fuselage structure situated along longitudinal sides of the landing gear casing. 
     
     
       9. A landing gear casing according to  claim 1  wherein the envelope structure comprises a curved longitudinal profile forming a fairing or shroud with an adapted shape to join an envelope of a profile of the retracted landing gear. 
     
     
       10. A landing gear casing according to  claim 9  wherein the envelope structure comprises a longitudinal and transversal curved surface for which the curvature is adapted to balance pressurization stresses that are applied onto the envelope structure. 
     
     
       11. An aircraft equipped with a landing gear casing according to  claim 1 . 
     
     
       12. An aircraft equipped with a landing gear casing according to  claim 1  wherein the envelope structure includes a contour that is flush with the frame of the chassis on an inside of the aircraft. 
     
     
       13. An aircraft according to  claim 12  wherein the envelope structure is a structure with a curved longitudinal profile forming a fairing or shroud with an adapted shape to be flush with an envelope of a profile of the landing gear when retracted. 
     
     
       14. An aircraft according to  claim 12  wherein the envelope structure is a structure with a longitudinal and transversal curved surface for which the curvature is adapted to balance pressurization stresses that are applied onto the envelope structure.